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P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il)
Reynolds number: 50,000
Max Cl/Cd: 23.23 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51dtip-il-50000-n5.txt
Download as CSV file: xf-p51dtip-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: P-51D TIP (BL215) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5047   0.10399   0.09756  -0.0341   1.0000   0.0505
 -10.250  -0.5056   0.09899   0.09264  -0.0373   1.0000   0.0503
 -10.000  -0.5078   0.09365   0.08735  -0.0409   1.0000   0.0498
  -9.750  -0.5127   0.08794   0.08171  -0.0453   1.0000   0.0495
  -9.500  -0.5208   0.08261   0.07643  -0.0492   1.0000   0.0488
  -9.250  -0.5323   0.07794   0.07178  -0.0521   1.0000   0.0480
  -9.000  -0.5486   0.07421   0.06806  -0.0532   1.0000   0.0478
  -8.750  -0.5692   0.07168   0.06554  -0.0515   1.0000   0.0468
  -8.500  -0.5890   0.06954   0.06335  -0.0489   0.9943   0.0464
  -8.250  -0.5885   0.06498   0.05850  -0.0513   0.9806   0.0468
  -8.000  -0.5830   0.06049   0.05366  -0.0533   0.9714   0.0474
  -7.750  -0.5768   0.05629   0.04906  -0.0542   0.9627   0.0478
  -7.500  -0.5648   0.05201   0.04426  -0.0551   0.9564   0.0480
  -7.250  -0.5536   0.04842   0.04018  -0.0548   0.9493   0.0487
  -7.000  -0.5358   0.04480   0.03596  -0.0550   0.9443   0.0500
  -6.750  -0.5210   0.04214   0.03260  -0.0541   0.9386   0.0543
  -6.500  -0.5004   0.04006   0.03043  -0.0543   0.9344   0.0596
  -6.250  -0.4746   0.03735   0.02716  -0.0543   0.9310   0.0617
  -6.000  -0.4485   0.03506   0.02433  -0.0540   0.9274   0.0639
  -5.750  -0.4214   0.03310   0.02201  -0.0536   0.9238   0.0667
  -5.500  -0.3909   0.03151   0.02031  -0.0539   0.9210   0.0712
  -5.250  -0.3605   0.03042   0.01896  -0.0545   0.9184   0.0818
  -5.000  -0.3269   0.02939   0.01772  -0.0550   0.9165   0.0886
  -4.750  -0.3035   0.02861   0.01677  -0.0539   0.9135   0.0927
  -4.500  -0.2861   0.02792   0.01603  -0.0524   0.9098   0.0980
  -4.250  -0.2671   0.02728   0.01526  -0.0512   0.9064   0.1057
  -4.000  -0.2479   0.02650   0.01451  -0.0503   0.9033   0.1199
  -3.750  -0.2354   0.02563   0.01390  -0.0484   0.8997   0.1533
  -3.500  -0.2380   0.02394   0.01336  -0.0448   0.8951   0.3322
  -3.250  -0.2398   0.02454   0.01532  -0.0359   0.8921   0.7080
  -3.000  -0.1523   0.02800   0.01852  -0.0332   0.8969   0.8845
  -2.750  -0.1081   0.02795   0.01810  -0.0363   0.8960   0.8998
  -2.500  -0.0670   0.02780   0.01762  -0.0395   0.8946   0.9081
  -2.250  -0.0473   0.02777   0.01740  -0.0388   0.8918   0.9154
  -2.000  -0.0152   0.02765   0.01707  -0.0406   0.8898   0.9187
  -1.750   0.0106   0.02758   0.01681  -0.0413   0.8876   0.9213
  -1.500   0.0182   0.02769   0.01684  -0.0387   0.8838   0.9255
  -1.250   0.0277   0.02779   0.01685  -0.0365   0.8808   0.9295
  -1.000   0.0500   0.02784   0.01680  -0.0366   0.8786   0.9318
  -0.750   0.0738   0.02790   0.01676  -0.0369   0.8764   0.9344
  -0.500   0.0975   0.02799   0.01677  -0.0372   0.8744   0.9372
  -0.250   0.1066   0.02818   0.01692  -0.0349   0.8714   0.9411
   0.000   0.1210   0.02837   0.01708  -0.0337   0.8690   0.9447
   0.250   0.1420   0.02856   0.01726  -0.0337   0.8669   0.9480
   0.500   0.1623   0.02876   0.01745  -0.0335   0.8646   0.9515
   0.750   0.1822   0.02898   0.01767  -0.0332   0.8624   0.9550
   1.000   0.2064   0.02923   0.01794  -0.0337   0.8609   0.9582
   1.250   0.2343   0.02952   0.01828  -0.0349   0.8597   0.9613
   1.500   0.2463   0.02986   0.01866  -0.0335   0.8568   0.9672
   1.750   0.2634   0.03018   0.01905  -0.0329   0.8540   0.9724
   2.000   0.2858   0.03055   0.01950  -0.0334   0.8521   0.9771
   2.250   0.3091   0.03093   0.02001  -0.0339   0.8500   0.9827
   2.500   0.3371   0.03135   0.02055  -0.0353   0.8480   0.9881
   2.750   0.3648   0.03181   0.02115  -0.0366   0.8464   0.9947
   3.000   0.3638   0.03220   0.02163  -0.0330   0.8422   1.0000
   3.250   0.3616   0.03250   0.02199  -0.0289   0.8373   1.0000
   3.500   0.3856   0.03289   0.02252  -0.0289   0.8324   1.0000
   3.750   0.3883   0.03310   0.02285  -0.0253   0.8226   1.0000
   4.000   0.4091   0.03340   0.02330  -0.0246   0.8130   1.0000
   4.250   0.4403   0.03379   0.02391  -0.0255   0.8056   1.0000
   4.500   0.4575   0.03412   0.02442  -0.0242   0.7948   1.0000
   4.750   0.5000   0.03401   0.02470  -0.0258   0.7788   1.0000
   5.000   0.5347   0.03353   0.02454  -0.0256   0.7570   1.0000
   5.250   0.5811   0.03210   0.02354  -0.0255   0.7283   1.0000
   5.500   0.6216   0.02820   0.01999  -0.0208   0.6649   1.0000
   5.750   0.6122   0.02823   0.02012  -0.0155   0.6176   1.0000
   6.000   0.5969   0.02937   0.02134  -0.0112   0.5587   1.0000
   6.250   0.6357   0.02736   0.01694  -0.0047   0.1838   1.0000
   6.500   0.6396   0.02913   0.01824  -0.0023   0.1349   1.0000
   6.750   0.6507   0.03066   0.01955  -0.0005   0.1118   1.0000
   7.000   0.6683   0.03204   0.02086   0.0009   0.0967   1.0000
   7.250   0.6903   0.03324   0.02209   0.0017   0.0790   1.0000
   7.500   0.7367   0.03483   0.02383   0.0010   0.0665   1.0000
   7.750   0.7815   0.03676   0.02593  -0.0006   0.0539   1.0000
   8.000   0.8208   0.03956   0.02883  -0.0018   0.0475   1.0000
   8.250   0.8532   0.04276   0.03256  -0.0019   0.0443   1.0000
   8.500   0.8737   0.04534   0.03537  -0.0015   0.0406   1.0000
   8.750   0.8889   0.04841   0.03874  -0.0006   0.0378   1.0000
   9.000   0.8989   0.05178   0.04267   0.0010   0.0360   1.0000
   9.250   0.9053   0.05540   0.04673   0.0027   0.0353   1.0000
   9.500   0.9065   0.05909   0.05082   0.0045   0.0350   1.0000
   9.750   0.9028   0.06276   0.05484   0.0064   0.0348   1.0000
  10.000   0.8939   0.06632   0.05868   0.0084   0.0347   1.0000
  10.250   0.8809   0.06993   0.06254   0.0103   0.0348   1.0000
  10.500   0.8653   0.07386   0.06667   0.0113   0.0349   1.0000
  10.750   0.8485   0.07808   0.07108   0.0115   0.0352   1.0000
  11.000   0.8293   0.08289   0.07604   0.0107   0.0354   1.0000
  11.250   0.8103   0.08821   0.08148   0.0090   0.0358   1.0000
  11.500   0.7910   0.09432   0.08769   0.0062   0.0362   1.0000
  11.750   0.7741   0.10099   0.09441   0.0025   0.0366   1.0000
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